By L. S. Fletcher
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Additional resources for Aerodynamic Heating and Thermal Protection Systems
10). Also, as is shown in Ref. 12, the normal pressure profiles are not influenced by radiation cooling. Consequently, the equations used to calculate the convective heating rates are influenced by radiation cooling primarily through the inviscid recovery enthalpy at the boundary-layer edge. 10 n/RN Fig. 556, 90-10 atm). 15 AEROTHERMAL ENVIRONMENT Figure 9 shows a comparison of the VSL and the approximate inviscid temperature profile at the end of the conical flank. These results are presented both with and without radiation.
The applicability of their technique to the present study is possible but difficult because of the complex geometry of the cavity and the seal gap. Kirlin and Schmitt5 investigated possible cove seal designs and measured cove heat-flux distributions on a cold prototype. In addition, they measured thermal response of a particular elevon cove seal design for the Space Shuttle Orbiter. They found that the heat flux to the cove increases with cove width, gas flow leakage rate, and elevon deflection.
B. , July 197U. Brewer, R. A. , May 1975. 7 Moss, J. N . , Anderson, E. C . , a n d B o l z , C. W . , "Aerothermal Environment for Jovian Entry Probes," AIAA Progress in Astronautics and Aeronautics: Thermophysics of Spacecraft and Outer Planet Entry Probes , Vol. 56, edited by A. M. Smith, 1977, PP- 333-35^. o Anderson, E. C. , Moss, J. N. , and Sutton, K. , "Turbulent Viscous-Shock-Layer Solutions With Strong Vorticity Interaction," AIAA Paper 76-120, Washington, D . C . , Jan. 1976; also Journal of Spacecraft and Rockets, Vol.
Aerodynamic Heating and Thermal Protection Systems by L. S. Fletcher
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